Bradford ECAPS's 50N HPGP Thruster is designed for attitude, trajectory and orbit control of larger satellites, including geostationary satellites, or launch vehicle applications. This thruster is currently in development and looking for partners to bring the prior work into fruition.

  • Propellant loading is simple, fast and avoids the cost associated with loading hydrazine. Allows the operator to spend less time on ground operations and more time on space operations.
  • ‘Fuel at the factory’ – be ready for launch vehicle integration upon arrival at the launch pad. Eliminates significant time and cost from lengthy pre-launch campaigns.
  • Non-toxic propellant is suitable for a new class of responsive small satellite launchers, where handling hazardous hydrazine may impede operations or where fully equipped hydrazine processing facilities may be non-existent at the launch site.
  • Higher performance over hydrazine allows for more payload or longer mission durations.
  • Allows for more secondary or ‘piggy-back’ launch opportunities, especially missions where there is concern about the hazards of hydrazine and its risks to the primary payload.
  • Allows for more agile mission profiles than electric propulsion. Spacecraft take significantly less time to execute maneuvers and orbit changes.

Specifications Table

Thruster Type HPGP
Propellant LMP-103S
Thrust Class 50 N
Primary Operational Mode Δ ∨
Inlet Pressure Range 5 - 26 Bar
Thrust Range 12.5 - 50 N
Nozzle Expansion Ratio 150:1
Steady State ISP (vacuum) Typical 2385 - 2500 Ns/Kg
(243 -255 s)
Density Impulse (vacuum) 2957 - 3100 Ns/L
Minimum Impulse Bit ≤ 2.5 Ns
Overall Length 327 mm
Mass 2.1 kg
FCV Type Solenoid
- No of Seats Dual Seat
- Pull-in Voltage 28 ± 4 VDC
- Holding Voltage 10 ± 1 VCD
- Coil Resistance (each coil) 64 Ω
Nominal Reactor Pre-heating Voltage 27 VDC
Regulated Reactor Ore-heating Power 75 - 100 W TBC
Target Life - Qual. Level  
Pulses 2,000
Propellant Throughput 50 kg
Longest Continues Firing 25 minutes
Accumulated Firing Time 1 hour
Firing Sequences 100
Demonstrated Life  
Pulses 160
Propellant Throughput 1.7 kg
Longest Continues Firing Time 10 seconds
Accumulated Firing Time 45 seconds
Firing Sequences 12
Maturation Level TRL 4
Current Status  
  Flight Like Model Designed